基于辐射加热的涡轮叶片热冲击试验方法  

Method of Turbine Blade Thermal Shock Test Based on Radiation Heating

作　　者：邱恒斌 武小峰 吴光耀 宫永辉 田玉坤 QIU Heng-bin;WU Xiao-feng;WU Guang-yao;GONG Yong-hui;TIAN Yu-kun(Beijing Institute of Structure and Environment Engineering,Beijing 100076,China;AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)

机构地区：[1]北京强度环境研究所,北京100076 [2]中国航发四川燃气涡轮研究院,成都610500

出　　处：《航空发动机》2024年第3期137-141,共5页Aeroengine

摘　　要：针对涡轮叶片热冲击试验的需求,提出了一种基于石英灯辐射加热的涡轮叶片热冲击试验方法。采用高功率双排石英灯进行辐射加热、氮气和水雾相结合进行主动冷却、伺服作动系统进行加热冷却循环运动控制。通过仿真计算分析了辐射加热方式和气雾结合冷却方式的可行性和有效性,并根据仿真结果开展了加热器、冷却设备设计,构建了基于石英灯辐射加热的涡轮叶片热冲击试验系统,实现了50次冷热循环的热冲击试验考核。结果表明:采用石英灯辐射加热和气雾结合降温的试验方法可以模拟涡轮叶片热冲击所需的温度场和升降温速率。基于石英灯辐射加热的热冲击试验方法有效、可靠,能够精确模拟叶片温度场,大部分特征点温度控制偏差均小于5%,可应用于涡轮叶片热冲击试验。Aiming at the requirement of a turbine blade thermal shock test,a method of turbine blade thermal shock test based on quartz lamp radiation heating was proposed.High-power double-row quartz lamps were used for radiation heating,the nitrogen and water mist were combined for active cooling,and a servo actuation system was used for heating and cooling cycle motion control.The feasibility and effectiveness of the radiation heating method and the nitrogen-water mist combined cooling method were analyzed by simulation.According to the simulation results,the heater and cooling equipment were designed,and the turbine blade thermal shock test system based on quartz lamp radiation heating was constructed,which realized the thermal shock test assessment of 50 thermal cycles.The results show that the test method of quartz lamp radiation heating and gas-mist combined cooling can simulate the temperature field and cooling rate required for the turbine blade thermal shock test.The thermal shock test method based on quartz lamp radiation heating is effective and reliable,which can accurately simulate the blade temperature field,and the temperature control deviation of most characteristic points is less than 5%,so it can be applied to turbine blade thermal shock tests.

关 键 词：涡轮叶片 热冲击 石英灯 辐射加热 试验方法 航空发动机 

分 类 号：V216.4[航空宇航科学与技术—航空宇航推进理论与工程]